2a952 Volume 5 Ures (2016)
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- 1.(801) The control surfaces that provide the aerodynamic force to maintain attitude and directional control of the aircraft include the ailerons,
- A.
Elevator, and control wheel
- B.
Elevator, and rudder
- C.
Elevator, and flaps
- D.
Flaps, and slats
- 2.(801) Which control surfaces provide aircraft roll control?
- A.
Ailerons and flight spoilers
- B.
Ailerons and lower rudder
- C.
Flight spoilers and rudder
- D.
Ailerons and rudder
- 3.(801) For high speed aileron operation, what surfaces are used in conjunction with spoilers for roll control?
- A.
Inboard ailerons only
- B.
Inboard elevators only
- C.
Outboard ailerons only
- D.
Both inboard and outboard ailerons
- 4.(801) Snubbers protect the ailerons from wind gusts in miles per hour (mph) up to
- A.
60 mph
- B.
70 mph
- C.
80 mph
- D.
90 mph
- 5.(801) Pitch control of the aircraft about the lateral axis is accomplished by the
- A.
Elevators
- B.
Ailerons
- C.
Rudders
- D.
Spoilers
- 6.(801) Which aircraft surface provides aircraft yaw control about the vertical axis?
- A.
Elevators
- B.
Ailerons
- C.
Spoilers
- D.
Rudder
- 7.(802) What are leading-edge and trailing-edge flaps used for?
- A.
Coordinated turns
- B.
Aileron augmentation
- C.
Landings and takeoffs
- D.
Pitch and yaw maneuvers
- 8.(802) How many leading edge flap surfaces are there?
- A.
18
- B.
22
- C.
26
- D.
30
- 9.(802) The priority valve permits flow only when hydraulic pressure in pounds per square inch (psi) exceeds
- A.
2500 ±300 psi
- B.
2500 ±500 psi
- C.
2000 ±300 psi
- D.
2000 ±500 psi
- 10.(802) The flap power package receives hydraulic pressure from the number
- A.
One and number two hydraulic systems
- B.
One and number four hydraulic systems
- C.
Two and number four hydraulic systems
- D.
Two and number three hydraulic systems
- 11.(802) What provides the electrical signal used for flap asymmetry control?
- A.
Comparator units
- B.
Flap power packages
- C.
Control cables and linkages
- D.
Flap position indicating system
- 12.(803) What is not included in the mechanical flight control system?
- A.
Cables
- B.
Torque tubes
- C.
Push-pull tubes
- D.
Electrically powered actuators
- 13.(803) What is not an advantage of the use of electro-mechanical actuators?
- A.
Reduces noise
- B.
Reduces weight
- C.
Eliminates the need for hydraulic fluid
- D.
Eliminates the need for electrical power
- 14.(804) What surface trims the aircraft about the pitch axis?
- A.
Horizontal stabilizer
- B.
Gear train
- C.
Ailerons
- D.
Flaps
- 15.(804) Release of either half of the stabilizer trim control switch will
- A.
Damage the auxiliary drive
- B.
Result in nose down travel
- C.
Stop the actuator motion
- D.
Result in nose up travel
- 16.(804) The stabilizer trim autopilot servomotor supplies power to move the stabilizer during
- A.
Ground operation only
- B.
High speed operation
- C.
Low speed operation
- D.
Autopilot operation
- 17.(804) What type of action does the actuator assembly convert rotary motion into for the purpose of controlling the stabilizer trim?
- A.
Nose left or nose right motion
- B.
Vertical motion
- C.
Linear motion
- D.
Rotary speed
- 18.(805) What flight control surface indicator is designed to display percentage of surface extension?
- A.
Flap/slat position indicator
- B.
Rudder trim position indicator
- C.
Aileron trim position indicator
- D.
Horizontal stabilizer trim position indicator
- 19.(805) Synchro position indicating systems convert mechanical shaft angles to
- A.
Mechanical shaft degrees
- B.
Electrical shaft degrees
- C.
Mechanical signals
- D.
Electrical signals
- 20.(805) What type of operating power is required by a selsyn position indicating system?
- A.
26 VAC
- B.
28 VDC
- C.
115 VAC
- D.
120 VDC
- 21.(805) The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned
- A.
45 degrees apart
- B.
90 degrees apart
- C.
120 degrees apart
- D.
180 degrees apart
- 22.(805) How accurately the selsyn position indicator rotor follows the transmitter depends upon the
- A.
Amplitude of the applied voltage
- B.
Frequency of the applied voltage
- C.
Spacing of the coils and taps
- D.
Strength of the rotor magnet
- 23.(806) Manual pitch and roll axis attitude adjustments are allowed by the
- A.
Flight control augmentation system (FCAS)
- B.
Stability augmentation system (SAS)
- C.
Flight management system (FMS)
- D.
Flight control set (FCS)
- 24.(806) The flight control set (FCS) pitch axis must be engaged for selection of altitude hold (ALT HOLD) or
- A.
Mach number hold (MACH HOLD)
- B.
Tactical air navigation (TACAN)
- C.
Navigation/localizer (NAV/LOC)
- D.
Heading select (HDG SEL)
- 25.(807) All signals needed for proper flight control set (FCS) operation are processed by the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Status/test panel
- 26.(807) Which component provides all switch holding voltages to the flight control set (FCS) control panel?
- A.
FCS controller
- B.
FCS processor
- C.
FCS status/test panel
- D.
Horizontal position sensor
- 27.(807) What condition is required to engage the flight control set (FCS) pitch axis?
- A.
Valid heading signal
- B.
Turn knob must be in detent
- C.
Valid selected gyro #1 and gyro #2 signals
- D.
Series yaw damper system must be engaged
- 28.(807) What condition is not required for flight control set roll axis engagement?
- A.
Valid heading signal
- B.
Turn knob must be in detent
- C.
Valid selected gyro #1 signal
- D.
Valid selected gyro #2 signal
- 29.(807) The status/test panel (STP) allows maintenance personnel to initialize and step through flight control set tests which are controlled by
- A.
Air data computer software
- B.
Analog to digital conversion
- C.
Flight control set processor software
- D.
Flight control set controller software
- 30.(807) The secondary goal of the flight control set continuous built-in-test (CBIT) is to isolate failures to a particular line replaceable unit (LRU) and store the information in the flight control set
- A.
Processor non-volatile memory
- B.
Controller non-volatile memory
- C.
Processor volatile random access memory
- D.
Controller volatile random access memory
- 31.(808) All characters on the flight control set (FCS) status/test panel (STP) are the result of display words sent from the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Disengage annunciator
- 32.(808) The flight control set (FCS) status/test panel (STP) provides personnel with an interface to the FCS
- A.
Disengage annunciator
- B.
Control panel
- C.
Processor
- D.
Controller
- 33.(808) Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to record an indicated failure in memory?
- A.
Right arrow (→)
- B.
Left arrow (←)
- C.
VERIFY
- D.
POWER
- 34.(808) Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to repeat a test?
- A.
POWER
- B.
VERIFY
- C.
Left arrow (←)
- D.
Right arrow (→)
- 35.(809) The component that enables the flight crew to engage and disengage the flight control set (FCS) is the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Status/test panel
- 36.(809) Engagement of the control panel ROLL axis switch causes the flight control set (FCS) to maintain the aircraft in a wings-level condition and
- A.
Maintain the prevailing pitch attitude
- B.
Maintain the prevailing yaw attitude
- C.
Hold the existing heading
- D.
Hold the existing altitude
- 37.(809) When the control panel NAV LOC switch is in the ON position, the flight control set (FCS) automatically
- A.
Flies down the glide slope beam path
- B.
Navigates along the selected course
- C.
Achieves Mach
- D.
Gains altitude
- 38.(809) The flight control set (FCS) control panel LOC ARM/CAP and G/S ARM/CAP indicators are controlled by the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Status/test panel
- 39.(809) When a flight control set (FCS) mode select switch is switched ON, a 28 VDC
- A.
Engage signal is sent to the flight control set processor
- B.
Disengage signal is sent to the flight control set processor
- C.
Engage signal is sent to the flight control set servo drum and bracket
- D.
Disengage signal is sent to the flight control set servo drum and bracket
- 40.(809) How many degrees of rotation do the flight control set (FCS) controller thumbwheels have?
- A.
90°
- B.
180°
- C.
270°
- D.
360°
- 41.(809) How many degrees of rotation does the flight control set (FCS) controller turn knob have?
- A.
90°
- B.
180°
- C.
270°
- D.
360°
- 42.(810) The flight control set (FCS) uses one servo motor to move the ailerons and one to move the
- A.
Slats
- B.
Rudders
- C.
Spoilers
- D.
Elevators
- 43.(810) What provides the only mechanical connection from the flight control set (FCS) servo motor to the aircraft control cables?
- A.
Horizontal position sensor
- B.
Servo drum and bracket
- C.
Jackscrew assembly
- D.
Trim actuator
- 44.(810) The component that provides a drive voltage to the flight control set (FCS) trim actuator is the FCS
- A.
Controller
- B.
Processor
- C.
Control panel
- D.
Status/test panel
- 45.(810) The flight control set (FCS) horizontal position sensor (HPS) consists of a
- A.
Trim actuator
- B.
Jackscrew assembly
- C.
Servo drum and bracket
- D.
Linear variable differential transformer
- 46.(811) What is the maximum bank angle in the flight control set (FCS) heading hold mode?
- A.
10 degrees
- B.
15 degrees
- C.
20 degrees
- D.
25 degrees
- 47.(811) What is the maximum bank angle in the flight control set (FCS) heading select mode?
- A.
10 degrees
- B.
15 degrees
- C.
20 degrees
- D.
25 degrees
- 48.(811) The flight control set (FCS) tactical air navigation (TACAN) mode will not advance to capture until the
- A.
Turn knob is in detent
- B.
Turn knob is out of detent
- C.
Glide slope (G/S) switch is on
- D.
Navigation/localizer (NAV/LOC) switch is off
- 49.(811) A prerequisite for entering the flight control set (FCS) localizer (LOC) capture mode is a valid
- A.
Radio altimeter signal
- B.
Glide slope signal
- C.
Air data signal
- D.
Mach signal
- 50.(812) What is the flight control set (FCS) pitch attitude limit?
- A.
10 degrees
- B.
15 degrees
- C.
20 degrees
- D.
25 degrees
- 51.(812) Which is not a command input the flight control set (FCS) pitch loop?
- A.
Mach hold signals
- B.
Glide slope signals
- C.
Altitude hold signals
- D.
Heading hold signals
- 52.(812) Flight control set (FCS) altitude hold cannot be engaged if the vertical velocity is greater than
- A.
3000 feet per minute
- B.
2500 feet per minute
- C.
2000 feet per minute
- D.
1000 feet per minute
- 53.(812) What provides information to the flight control set processor (FCSP) to produce an error signal when the aircraft goes above or below the engaged Mach number?
- A.
Radio altimeter
- B.
Air data computer
- C.
Glide slope receiver
- D.
Inertial navigation unit
- 54.(812) The flight control set (FCS) glide slope mode will disengage when the beam has been captured if selecting
- A.
Navigation/localizer
- B.
Heading select
- C.
Altitude hold
- D.
Test
- 55.(812) The flight control set (FCS) pitch thumbwheels, Mach hold, and altitude hold are disabled in
- A.
Glide slope capture mode
- B.
Localizer capture mode
- C.
Glide slope arm mode
- D.
Localizer arm mode
- 56.(813) From any initial rudder position, the series yaw damper (SYD) can command a
- A.
Maximum of four degrees left or right rudder deflection
- B.
Minimum of four degrees left or right rudder deflection
- C.
Maximum of six degrees left or right rudder deflection
- D.
Minimum of six degrees left or right rudder deflection
- 57.(814) When is the parallel yaw damper system intended to be operated?
- A.
Only during flight
- B.
Only during flight and taxi
- C.
Only during flight, takeoff, and landing
- D.
During flight, taxi, takeoff, and landing
- 58.(814) The parallel yaw damper system can only be engaged when the series yaw damper (SYD) is
- A.
Engaged
- B.
Disengaged
- C.
In test mode
- D.
In standby mode
- 59.(814) Which component of the parallel yaw damper system provides the necessary signals to stabilize the aircraft in the yaw axis?
- A.
Yaw damper control panel
- B.
Plug-in modules
- C.
Power supply
- D.
Rate gyro
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